Introduction to the magnetic field experiments designed by space technology laboratories, inc.
Explorer VI satellite observations and experiments on geomagnetic field termination, distortion, and storm time fluctuations
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Explorer VI satellite observations and experiments on geomagnetic field termination, distortion, and storm time fluctuations
Performance test evaluation of nickel-cadmium Nimbus secondary spacecraft cells
Functional acceptance tests of six ampere-hour adhydrode nickel cadmium secondary spacecraft batteries
Silicon drift field and thin single crystal cells, including cell for use on lightweight weather balloon panels
Performance of sealed nickel-cadmium spacecraft batteries with high overcharge capability
Electromagnetic interference and susceptibility testing of multicoder compliance to radio interference requirements
Low temperature, high temperature, and function tests of flow check valve for Apollo access arm
Test data summarized for pressure switch
Performance test results on position indicator
Acceptance testing of four ampere hour flooded sealed nickel-cadmium secondary spacecraft cells
Performance test data for dual ball shutoff valve
Silver-cadmium secondary spacecraft cell acceptance tests
Acceptance tests of nickel cadmium spacecraft cells with auxiliary electrodes for charge control
A preliminary evaluation of environmental capabilities was undertaken on toggle switches and on Apollo-type toggle switches. The purpose of this evaluation was to take a first look at their tested capabilities for the purpose of determining whether the candidate hardware appears to have a good chance of successfully completing a detailed envrionmental qualification test program.
A summary is presented of the additional development work on the existing ML Series concentrating solar collector for use with solar heating and cooling systems. The report discusses the intended use of the final report, describes the development hardware, lists deliverable end items, deals with problems encountered during fabrication and testing, and includes certification statements of performance. This report shows that the products developed are marketable and suitable for public use.
The solar heating system for space heating a 97,000 square foot building which houses administrative offices, assembly areas, and warehouse space is summarized. Information on system description, test data, major problems and resolutions, performance, operation and maintenance manual, manufacturer's literature, and as-built drawings is presented.
Results of tests show that all channels of all instruments, except channel 3 of the Biometer Mark 2, were stable in response to input signals were linear, and were adequately stable in response to temperature changes. The Biometer Mark 2 is labelled with an inappropriate description of the units measured and the dynamic range is a inappropriate for field measurements causing unnecessarily high fractional errors. This instrument is, therefore, quantization limited. The dynamic range and noise performance of the Model 12-1000 are appropriate for remote sensing field research. The field of view and performance of the Model 100A and the Model 12-1000 are satisfactory. The Biometer Mark 2 has not, as yet, been satisfactorily equipped with an acceptable field of view determining device. Neither the widely used aperture plate nor the 24 deg cone are acceptable.
Noise reduction is mostly limited to light helicopters whose noise signature is dominated by their tail rotors. It is primarily hardware oriented. Well known noise reduction techniques such as reduction of rotor speeds with an accompanying increase in solidity to maintain performance, engine noise reduction with the use of exhaust mufflers, and acoustic blanketing of transmission and engine compartment are used. The concept of blade phasing as a means of reducing tail rotor noise is also used. Engine noise (exhaust noise), power train noise and airframe noise becomes important at low rotor tip speeds and means must be found to reduce these noise sources if further noise reductions are desired. The use of a special test rig aids in isolating the various noise sources and arriving at the penalties (performance or payload) involved in quieting them. Significant noise reduction are achieved for the light helicopter with minimum performance or weight penalties because of the dominance of a single noise source (the tail rotor).